17 Matching Results

Search Results

Results: 1 - 17
open access

Approximate Stress Analysis of Multistringer Beams With Shear Deformation of the Flanges

Description: "The problem of the skin-stringer combinations used as axially loaded panels or as covers for box beams is considered from the point of view of the practical stress analyst. By a simple substitution the problem is reduced to the problem of the single-stringer structure, which has been treated in NACA Report no. 608. The method of making this substitution is essentially empirical; in order to justify it, comparisons are shown between calculations and strain-gage tests of three beams tested by th… more
Date: April 20, 1938
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department
open access

Theoretical stability and control characteristics of wings with various amounts of taper and twist

Description: From Summary: "Stability derivatives have been computed for twisted wings of different plan forms that include variations in both the wing taper and the aspect ratio. Taper ratios of 1.0, 0,50, and 0.25 are considered for each of three aspect ratios: 6, 10, and 16. The specific derivatives for which results are given are the rolling-moment and the yawing-moment derivatives with respect to (a) rolling velocity, (b) yawing velocity, and (c) angle of sideslip. These results are given in such a for… more
Date: April 19, 1938
Creator: Pearson, Henry A. & Jones, Robert T.
Partner: UNT Libraries Government Documents Department
open access

Tests of Two Full-Scale Propellers With Different Pitch Distributions, at Blade Angles Up to 60 Degrees

Description: "Two 3-blade 10-foot propellers were operated in front of a liquid-cooled engine nacelle. The propellers differed only in pitch distribution; one had normal distribution (nearly constant pitch for a blade angle of 15 degrees at 0.75 radius), and the other had the pitch of the tip sections decreased with respect to that for the shank sections (blade angle of 35 degrees for nearly constant pitch distribution). Propeller blade angles at 0.75r from 15 degrees to sixty degrees, corresponding to desi… more
Date: April 14, 1938
Creator: Biermann, David & Hartman, Edwin P.
Partner: UNT Libraries Government Documents Department
open access

Model Study of Plans for Channel Improvement at Dogtooth Bend, Mississippi River, Folder 1

Description: This memorandum, constitutes a report on the results of experiments conducted at the U. S. Waterways Experiment Station on a small scale model of that reach of the Mississippi River near and including Dogtooth Bend (Mile 32.7 above to Mile 4.0 below Cairo).
Date: April 2, 1938
Creator: Waterways Experiment Station (U.S.)
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a 4-Engine Monoplane Showing Effects of Enclosing the Engines in the Wing and Comparisons of Tractor- and Pusher-Propeller Arrangements

Description: Report presenting testing in the full-scale wind tunnel on a model of a large 4-engine monoplane to determine the overall aerodynamic efficiency of a conventional wing-nacelle-engine installation as compared with power-plant installations enclosed in the wing with extension shafts to the propellers. Results regarding power-on and power-off performance for the installations as well as propeller noise are provided.
Date: April 1938
Creator: Silverstein, Abe & Wilson, Herbert A., Jr.
Partner: UNT Libraries Government Documents Department
open access

The design of floats

Description: Following a summary of the multiplicity of domestic and foreign floats and a brief enumeration of the requirements of floats, the essential form parameters and their effect on the qualities of floats are detailed. On this basis a standard float design is developed which in model families with varying length/beam ratio and angle of dead rise is analyzed by an experimental method which permits its best utilization on any airplane.
Date: April 1938
Creator: Sottorf, W.
Partner: UNT Libraries Government Documents Department
open access

Engine performance and knock rating of fuels for high-output aircraft engines

Description: From Summary: "Data are presented to show the effects of inlet-air pressure, inlet-air temperature, and compression ratio on the maximum permissible performance obtained on a single-cylinder test engine with aircraft-engine fuels varying from a fuel of 87 octane number to one 100 octane number plus 1 ml of tetraethyl lead per gallon. The data were obtained on a 5-inch by 5.75-inch liquid-cooled engine operating at 2,500 r.p.m. The compression ratio was varied from 6.50 to 8.75. The inlet-air te… more
Date: April 1938
Creator: Rothrock, A. M. & Biermann, Arnold E.
Partner: UNT Libraries Government Documents Department
open access

Flight and wind-tunnel tests of an XBM-1 dive bomber

Description: From Summary: "Results are given of pressure-distribution measurements made in flight over the right wing cellule and the right half of the horizontal tail surfaces of a dive-bombing biplane. Simultaneous measurements were also taken of the air speed, control-surface positions, control forces, and normal accelerations during various abrupt maneuvers in vertical plane. These maneuvers consisted of push-downs and pull-ups from level flight, dives and dive pull-ups from inverted flight. Besides th… more
Date: April 1938
Creator: Donely, Philip & Pearson, Henry A.
Partner: UNT Libraries Government Documents Department
open access

The Focke helicopter

Description: This report presents some of the problems concerning tests of helicopters, such as forced landings, controllability and stability, general safety, piloting maneuvers, performance, servicing, and the production of lift of a propeller. Test flights are described including a 67.67 mph flight by Hanna Reitsch.
Date: April 1938
Creator: Focke, H.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Ignition and Combustion Processes of Diesel Engines Operating With Turbulence and Air-Storage Chambers

Description: The flame photographs obtained with combustion-chamber models of engines operating respectively, with turbulence chamber and air-storage chambers or cells, provide an insight into the air and fuel movements that take place before and during combustion in the combustion chamber. The relation between air velocity, start of injection, and time of combustion was determined for the combustion process employing a turbulence chamber.
Date: April 1938
Creator: Petersen, Hans
Partner: UNT Libraries Government Documents Department
open access

The Lift Distribution of Wings With End Plates

Description: The object of the present report is to ascertain the relationship of the circulation distribution over the wing and of the lift to the height and position of the end plate. The side forces and moments on the end plates were also determined. It is found that moving an end plate of certain length up from the symmetrical position, is followed by a slight increase of the total lift.
Date: April 1938
Creator: Mangler, W.
Partner: UNT Libraries Government Documents Department
open access

Model Experiments on the Forces and Moments Acting on an End Plate Fitted to a Wing

Description: "This paper reports on 4-component balance measurements with and without angle of sideslip made on an airfoil with end plate at one tip. In addition, pressure distribution measurements on the end plate served as a basis for the determination of the forces on the end plate and for the bending moments" (p. 1).
Date: April 1938
Creator: Schrenk, O.
Partner: UNT Libraries Government Documents Department
open access

A new spinning-test method

Description: This report contains a description of a new spinning-test arrangement wherein the otherwise customary rotation of the model about a fixed axis is abandoned in favor of a corresponding rotation of the air stream. The advantage of this method lies in the fact that the model is at rest while the spin is recorded. In this manner it is possible to secure systematic results with little loss of time while employing 3- or 6-component wind-tunnel balances. The troublesome equalization of the mass forces… more
Date: April 1938
Creator: Kramer, M. & Krüger, K. B.
Partner: UNT Libraries Government Documents Department
open access

Some Aspects of the Stalling of Modern Low-Lying Monoplanes

Description: The factors affecting the stalling characteristics of modern airplanes are briefly discussed. The effect of present-day design trends is shown and means for improving the stalling characteristics of future airplanes are indicated.
Date: April 1938
Creator: Soulé, Hartley A. & Gough, Melvin N.
Partner: UNT Libraries Government Documents Department
open access

A study of flying-boat take-off

Description: It is shown that the normal resistance curve for a flying boat may be approximated by two straight lines. The equations for take-off distance and time, derived from this approximation, are applied to a series of flying boats and the resulting factors are plotted in non dimensional form in a series of charts. Take-off performances from the charts are shown to be in good agreement with step-by-step integrations. Some applications of the charts to the solution of general design problems are includ… more
Date: April 1938
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of a 2-Engine Airplane Model as a Preliminary Study of Flight Conditions Arising on the Failure of the Engine

Description: "Wind tunnel tests of a 15-foot-span model of a two-engine low wing transport airplane were made as a preliminary study of the emergency arising from the failure of one engine in flight. Two methods of reducing the initial yawing moment resulting from the failure of one engine were investigated and the equilibrium conditions were explored for two basic modes on one engine, one with zero angle of sideslip and the other with several degrees of sideslip. The added drag resulting from the unsymmetr… more
Date: April 1938
Creator: Hartman, Edwin P.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen